Aircraft



G. CLARK Nov. 22, 1932.

AIRCRAFT Filed July 2, 1931 5 Sheets-Sheet Xvveytor 0281x14 G. CLARK,

Nov. 22, 1 932.

AIRCRAFT Filed July 2. 1951 3 Sheets-Sheet 3 Patented Nov. 22, 1932 UNITED STATES PATENT"- OFFICE GEORGE own, or snronmAcE, mANrroB eANAnA AIRcaArr Application filed an a, 1931. Serial in. 548,436.

pressure to the foils to be discharged through the outlets thereof and in a direction and manner such that .an area of low air pressure is created on the top side of the wing and an area of high air pressure is created on the under side ofthe wing and the result-- ant of such pressures creates lift and flight.

A further object is to arrange the air foils with air spaces therebetween and with the leading edge of the following foil overlying 0 the trailing edge of the foil in advance thereof and to position the foils in respect to one another so that the inclination to the horizontal of the several air passages gradually diminishes in passing rearwardly of the wing and further to design the foils of a stream line cross section and suchthat each foil has a longitudinally extending air escape slot in its trailing edge of predetermined width.

A further object of the invention is to design the structure so that the velocity and pressure of the air passing from the blower to the several foils and-through the foils to the slots, can be maintained at a pressure and velocity for most effectively obtaining flight and lift. 7

With the above more important and other minor objects in view which will become more apparent as the description proceeds, the invention consists essentially in the arrangement and construction of parts hereinafter more particularly described, reference being had to the accompanying drawings, in which Fig. 1 is a lan view of the machine. Fig. 2 is a ront end view. Fig. 3 is a side view. Fig. 4 is an enlar ed detailed vertical sectional view. at 44 igure 1.

Fig. 5 is a vertical cross sectional view at Fig. 5-5 Figure 4.- i

F ,6 is an enlarged detailed cross sectional view at 6-6 Figure 1.-

Fig. 7 'is a sectional view at 77 Figure g In the drawings like characters of reference indicate corresponding parts in the several figures.

The machine herein shown isof the well known monoplane type but it is to be distinctly understood that the improvements herein disclosed in regard to such type of machlne, can be embodied with equal facility in various other types of power driven heavier. than air machines and also in those forms of aircraft's known as gliders.

known stream line form and is provided rearwardly with the customary vertical fin 2, rudder 3, horizontal stabilizer 4, elevator 5 and tail skid 6, these forming no part of the present invention so that they are not further described. The fuselage embodies, forward- ,ly, a cabin 6 containing the aviators seat 7 and as the details of such parts may vary,

The fuselage 1 of the machine is of the well G5 they are not herein described at length. In

advance of the cabin, the fuselage contains a power driven centrifugal blower and this 1s utilized to direct a blast of air to and through the several foils of the wings which are of the novel type of construction'hereinafter described in detail. Astationary bearing 8 is suitably carried say bythe front wall of the cabin and the forward end of the fuselage supports a dished inlet ring 9 which supports centrally ward end of which is mounted the engine 13 of any approved design, the engine rotating the shaft when in use. The. shaft carries a rear circular plate 14: permanently secured to the shaft to rotate therewith and the plate I carries a plurality of forw'ardly extending 5 similar equi-spaced blades 15 which have their forward ends securedpermanently to anannular disc 16 located directly to therear of the ring. Spokes l7 vextend between the H disc 16 and the shaft.

It will be observed that the blades converge m0 rearwardly so that they surround an inner frusto-conical shaped air space, the forward end of which communicates with atmosphere through the ring 9 and the rear end of which is closed by the plate 14. The fan formed by a the discs and blades is obviously directly driven by the engine and atmospheric air will be drawn into the conical area within the blades and expelled outwardly between the blades upon the fan being driven by the oni gine in the direction of the applied arrow Figure 5. The air discharged by the blades is directed by air ducts 18 and 19 to the inner ends of the wings 20 and 21 and the design of the air ducts is so proportioned as to afford a the maximum recovery from velocity pressure to static pressure with the least amount of turbulence, the air flowing evenly and smoothly in the air ducts to the wings.

It .n'iight be here mentioned that the inlet ring 9 is of stream line design thereby reducing air entering losses to a minimum and that the impeller or wheel of the blower which embodies the discs and the blades is designed so as to keep a uniform Velocity of air a through the wheel and thereby reduce wheel loss.

From the above, it will be apparent that I have provided a forwardly disposed power driven centrifugal blower or fan of the multiblade type which is so mounted in the front part of the fuselage or other desirable point that the intake opening faces the directionof forward motion of the aircraft and the air it will be observed also that the leading edge of each air foil overlies and is spaced from the trailing edge of the one in advance. The air foils are of stream line in shape and the trailing edge of each air foil is provided with a lengthwise extending slit or slot 23 of prop- 'er size to give egress to the contained air.

It will be observed that the forward air foils are disposed at a greater angle to the horizontal than the rear air foils, the angles graduallydiminishing from front to rear of the wing with the result that there is a gradual change in the direction of the air 00 blast from front to rear of the wing, the,

blast from the front foil discharging downwardly and rearwardly at a considerable angle and that from the rear foil discharging almost horizontally and rearwardly. It is to be also noticed that the cross sectional area of the foils gradually diminishes in passing outwardly from the fuselage towards the tips thereof so that an even distribution and constant velocity of air through the slots of the foils is maintained.

The several foils of each wing are suitably fastened to reinforcing bands 24 and 25 and the wing as a whole is braced by stay wires 26 extending between the band 24 and the top of the cabin. Each wing is provided with an aileron 27 of well known design, thecontrols of which are not herein shown. The forepart of the fuselage is supported by an under carriage 28 of any approved design.

From the above, it will be apparent that I have provided a heavier than air aircraft of improved design wherein the wings are formed each from a plurality of spaced hollow air foils' having rear air outlets, air

under pressure being supplied to the foils by a power driven blower mounted on the machine and expelled from the foils through the slits of the foils.

When the machine is in operation, the arrangement is such that I create a low pressure area above the wings and a high pressure area below the same which is obviousl very desirable. The air discharging at high velocity from the air foils creates a high pressure area underneath the wings and also induces secondary air currents to flow through the spaces between the individual air foils, the effect of which not only reduces the air pressure on the upper side of the wing but increases the air pressure on the under side of the foils. The forward and upward inclination of the space in between the air foils together with the downward and backward discharge of air from the trailing edge of each foil re-acts to give :1 eneral upward and forward motion to the w ole craft which results in lift and flight when sufficient power is applied to induce the required difference in pressure between the upper and lower faces of the wings.

It is b lieved that the lift component enerated w iill be greatly in excess of the rag component so that the resultant force will work more nearly vertical than is possible with the popular designs now at present in use. Attention is directed also to the fact that the application of power to an aeroplane by this means utilizes the full available and useful power of the machine to the majorit of the lifting area direct and at a static position and it is accordingly expected that the aeroplane provided with my invention will rise from the ground without'the necessit of first attaining a horizontal velocity su ficient to be transposed into lift as is common practice at present.

While I have shown the machine as power driven, I might point out that the invention can be used to advantage in gliders where it would not be necessary to provide the engine and the wheel driven thereby provided the glider had reached suflicient elevation and was gliding. It will be apparent that the air entering through the disc 9 at a high velocity will be distributed to the foils in the same manner as hereinbefore described and will have much the same effect in producing an area of high air pressure on the under side of the wings and an area of low air pressure on the top side thereof.

What I claim as my invention is 2-- '1. In'a heavier than air aircraft, a wing formed from a plurality of hollow spaced air foils extending longitudinally of the wing and having the leading edge of a following foil overlying the trailing edge of the foil in advance thereof and the trailing edges of the foils provided with restricted air outlets and means for directing air under pressure to the interior of the foils.

2. In a heavier thanair aircraft, a wing formed from a plurality of hollow spaced air I foils extending lon itudinally of the wing and having the 'lea ing' edge of a following foil overlying the trailing edge of the foil in advance thereof and the trailing edges of the foils provided with restricted air outlets and the several'foils set at varying angles to the horizontal plane and means, for admitting air under pressure to the-interior of the foils. 3. In a. heavier than airaircraft, a wing formed to provide a plurality of spaced longitudinally extending hollow air foils having restricted air outlets provided in their trailing edges and a power driven blower communicating with the foils of the wing to deivitlar air under pressure to the interior of the o s.

4. In a heavier than air aircraft, a wing formed from 'aplurality of spaced hollowv foils receiving air under pressure and having restricted air outlets, the foils being disposed in relation one to the other thatthe' air dis charging through the outlets causes an area ly in advance thereof and having the trailing edge of each foil provided with a restricted air outlet passage and means for admitting air under pressure to the several foils.

7. A heavier than air aircraft having the wings thereof each formed fro-m a plurality of spaced hollow air foils extending longitudinally of the wing and positioned with the leading edge of any foil overlying the trailing edge of the foil directly in advance there,

of and having the trailing edges of the foils provided with'restricted air outlets and an air chamber communicating with the foils and having the forward end thereof open to gather and direct air under pressure to the foils when the aircraft is in flight.

8. A heavier than air aircraft having the wings thereof each formed from a plurality of spaced hollow air foils extending longitudinally of the wing and positioned with the leading edge of any foil overlying the trailing edge of the foil directly in advance thereof and having the trailing edges of the foils provided with restricted air outlets and a power driven air blower mounted on the aircraft and communicating with the interior of the foils.

Signed at Winnipeg, this 5th day of June,

GEORGE CLARK.

of increased pressure onthe under side of the I wing and an area of decreased pressure on the top side thereof.

.5. In a heavier than air aircraft, a wing formed from a plurality of longitudinally extendingspaced hollow air foils'of stream line cross section and positioned with the leading edge of any following foil overlying the .trailing'edge of the foil directly in advance thereof and having the trailing edge of each foil provided with a restricted air outlet passage and means for admitting air under. pressure to the several foils. v

6. In a heavier than air aircraft, a wing formed from a plurality of longitudinally extending spaced hollow air foils of stream line cross section. and gradually diminishing in cross sectional area from their inner ends outwardly to the tip of the wing and positioned with the leading edge of any following foil overlying the trailing edge of the foil direct- 

